Closure system for a support structure

ABSTRACT

System for opening and closing a structural part arranged on a support structure. The system includes at least one hinged joint device for flexibly connecting the structural part to the support structure. The at least one hinged joint device is arranged inside the support structure and has an axis of rotation about which the structural part can be pivoted relative to the support structure during opening and closing. A locking arrangement is structured and arranged to connect the structural part to the support structure in a form-locking manner when the structural part is in a closed position. In the closed position, the locking arrangement is arranged to relieve the at least one hinged joint device. This Abstract is not intended to define the invention disclosed in the specification, nor intended to limit the scope of the invention in any way.

CROSS-REFERENCE TO RELATED APPLICATIONS

The present application is a continuation application of parent U.S.patent application Ser. No. 10/943,251 filed on Sep. 17, 2004, now U.S.Pat. No. 7,503,523 the disclosure of which is expressly incorporated byreference herein in its entirety. The present application also claimspriority under 35 U.S.C. §119 of German Patent Application No. 103 43627.8, filed on Sep. 20, 2003, the disclosure of which is expresslyincorporated by reference herein in its entirety.

BACKGROUND OF THE INVENTION

1. Field of the Invention

The invention relates to a closure device for a support structure thatis, e.g., an area of the outer contour of an aircraft that can be openedand closed for the purpose of access.

2. Discussion of Background Information

In aircraft, such closure devices are provided, in particular, ashatches for maintenance and inspection purposes, as a radome, as apassenger or cargo compartment door, or for a similar purpose. If such aclosure device is provided for maintenance or inspection purposes, it isoften necessary for it to be possible for these parts of the outercontour to be opened and closed more or less quickly, which is the caseanyway with a passenger or cargo compartment door. It is therebyessential, in particular, if the aircraft is a high-speed aircraft, thatthe aerodynamic outer contour is only slightly impaired thereby and thatthe mechanical connection to the rest of the structure of the aircraftreliably withstands the operating loads occurring.

Very different solutions have hitherto been realized for such closuredevices, whereby most of the mechanisms comprise hinge elements andlocking elements of different types. Depending on the required openingangle of the closure device, and the necessity of integrating it intothe structure of the aircraft as a supporting element, very solid hingessometimes result. The closure devices are often embodied by lockingelements in the form of hooks or shear pins.

If the aircraft is a combat aircraft, expensive measures are often takento damp the radar reflection values in the area of the closure devices,i.e., at the hinge, the lock and at gaps or steps at the transitionbetween the closure device and the rest of the outer skin of theaircraft. Moreover, these locations are more or less responsible foraerodynamic resistance and thus for the fuel consumption of theaircraft.

SUMMARY OF THE INVENTION

The invention aims to provide an improved closure device of the typementioned.

This aim is attained by providing a closure device having one or more ofthe features described below. Advantageous further developments of theclosure device according to the invention are also described herein.

According to the invention, a closure device is created for an area ofthe outer contour of an aircraft which can be opened and closed for thepurpose of obtaining access. The closure device has a hinge throughwhich the closure device is connected to the structure of the aircraftand about which the closure device can be pivoted between an openedposition and a closed position. It also has a locking device with whichthe closure device can be locked against the structure of the aircraftin the closed position. According to the invention, the hinge isarranged inside the outer contour of the aircraft and has a virtual axisof rotation located outside the outer contour of the aircraft. It isabout this axis that the closure device is pivoted during opening andclosing. The locking device is embodied such that in the closed state itconnects the closure device to the structure of the aircraft in aform-locking manner. In this way, the locking device essentiallycompletely relieves the hinge.

One advantage of the closure device according to the invention is thatit guarantees improved aerodynamic properties of the aircraft. This isbecause it manages to do so without a hinge lying on the outside.Another advantage is that the static properties of the connection areimproved. Furthermore, gaps and steps are reduced or avoided in theaircraft structure, which is conducive to a reduction of the aerodynamicresistance and, if desired, of the radar echo. A further importantadvantage is that, in the closed state of the closure device, the hingesdo not bear the operating loads and can thus be built in a relativelylight manner. A further advantage is the small space requirement for theinvention and the great compactness of the closure device. Another veryimportant advantage is that there is a very low risk of blocking theclosure device, so that it is fail-safe and works effectively.

According to the invention, a closure device for opening and closing astructural part arranged on a support structure, with at least onehinged joint device for the flexible connection of the body part to thestructural part and with a locking device with which the closure devicecan be locked in the closed position, is provided. The at least onehinged joint device is arranged inside the vehicle structure and has anaxis of rotation of the structural part about which the same can bepivoted during opening and closing. The axis of rotation is located onthe side to which the structural part can be pivoted for opening. Thelocking device is embodied such that in the closed state it connects thestructural part to the support structure in a form-locking manner whilerelieving the hinged joint device.

The locking device can comprise at least one first flange that can bearranged on the structural part and at least one second flange that canbe arranged on the support structure and that interacts with the firstflange. A blocking device interacts with first and second flanges suchthat in the closed position it provides a form-closed locking betweenthe first flange and the second flange. The locking device also has atightening mechanism with which the blocking device can be tightened orreleased on or relative to the flanges.

The hinged joint device can include two legs flexibly coupled to oneanother, wherein the first leg is attached to the structural part andthe second leg is attached to the support structure. The joint axis thatconnects the two legs to one another can run in the direction of theaxis of rotation of the closure device. Alternatively, the hinged jointdevice can include two legs which are flexibly coupled to one anotherwith a first axis, a second axis and a center axis, wherein these axesintersect at a point located on the axis of rotation of the closuredevice.

The first flange and the second flange can respectively form a curverunning in a completely closed manner. The first flange and/or thesecond flange can also act to limit the outer circumference of a passageopening that can be closed by the closure device. Furthermore, the firstand second flange can be circular, oval or composed of several parts ofcircular and/or oval flanges.

The first and second flange can respectively lie in one plane. The partsof circular and/or oval flanges of which the first and second flange arerespectively composed can lie in different planes that intersect wherethe parts of the flange touch one another.

The blocking device can be formed by a chain or belt arrangement forlocking the first and second flange. In the closed state of the closuredevice, the chain or belt arrangement can be arranged to run radiallyoutside and around the circumference of the first and second flange. Onsides facing one another, the first and second flange respectivelyfeature stop surfaces that rest against one another when the closuredevice is closed. The flanges also feature first locking surfaces onsides facing away from one another. The chain or belt arrangementincludes a number of clamp elements that feature respective secondlocking surfaces interacting in a form-locking manner with the firstlocking surfaces provided on the first and second flanges. The chain orbelt arrangement has a tightening mechanism with which the chain or beltarrangement is adjustable in its length for releasing or tightening thesame between an extended and/or expanded state in which the firstlocking surfaces of the first and second flanges and the second lockingsurfaces of the clamp elements are free of one another so as to releasethe closure device, and a contracted and/or retracted state in which thefirst locking surfaces of the first and second flanges and the secondlocking surfaces of the clamp elements are fixed against one another tolock the closure device.

Alternatively, the blocking or locking device can be composed of a chainarrangement which enables the locking of the first and second flange,wherein in the closed state of the closure device, the arrangement isarranged to run around the circumference of the first and second flange.The first and second flanges respectively feature stop surfaces on sidesfacing one another that rest against one another when the closure deviceis closed and first locking surfaces on sides facing away from oneanother. The flexible chain arrangement includes a number of clampelements which feature respective second locking surfaces interacting ina form-locking manner with the first locking surfaces provided on thefirst and second flanges. The chain arrangement features a tighteningmechanism with which the chain arrangement is adjustable in its radiallength between a first position in which the first locking surfaces ofthe first and second flanges and the second locking surfaces of theclamp elements are free of one another to release the closure device,and a second position in which the first locking surfaces of the firstand second flanges and the second locking surfaces of the clamp elementsare fixed against one another to lock the closure device.

The chain arrangement can be arranged to run radially outside around thecircumference of the first and second flanges, whereby in the firstposition, the closure device is released and the clamp elements of thechain arrangement adopt a position lying radially further outwards, andwhereby in the second position, the closure device is locked and theclamp elements adopt a position lying radially further inwards.Alternatively, the chain arrangement can be arranged to run radiallyinside the first and second flanges, whereby, in the first position, theclosure device is released and the clamp elements of the chainarrangement adopt a position lying radially further inwards and in thesecond position the closure device is locked and the clamp elementsadopt a position lying radially further outwards.

The first locking surfaces can form an outer conical cross-sectionalshape which tapers outwards, and the second locking surfaces can form aninner conical cross-sectional shape which taper outwards and whichmatches the former during locking.

The chain or belt arrangement can be arranged in a fixed manner withrespect to one of the first or second flanges and on the side facing theother flange. The clamp elements can feature a sliding block surfacetilted outwards by way of which the clamp elements can be displacedradially outwards during closing of the closure device. This can occurthrough the other flange in order to engage the first locking surface ofthe other flange behind the assigned second locking surface of the clampelements.

The tightening mechanism can include a thread tightener which actsbetween respective opposite ends of the chain or belt arrangement and ahelical gear for operating the same. The helical gear contains a gearwheel coupled to the thread tightener and a worm wheel coupled to adrive element. The drive element can thereby be a hand twist grip. Thehand twist grip can be coupled to the worm wheel via a ball lock thatcan be unlocked by way of a separate operating element. This can occur,in particular, by way of a push button. Furthermore, the hand twist gripcan be displaceable in the direction of its axis of rotation between alowered position, in which it is secured against rotation, and a raisedor not lowered position in which it is released for rotation. A springcan be provided through which the hand twist grip is displaced duringunlocking by the ball lock from the lowered position into the raised ornot lowered position.

The tightening mechanism can also contain a pressure hose arrangedbetween the clamp elements and a contact surface lying radiallydisplaced thereto. The hose can be acted on by a hydraulic or pneumaticdrive medium. A pressure medium pump is connected to the pressure hosefor feeding the drive medium to the pressure hose. In this way, actingon the pressure hose with the drive medium creates a cross-sectionalenlargement of the pressure hose and causes a radial displacement of theclamp elements from the first position to the second position in orderto lock the closure device. Draining the drive medium from the pressurehose produces a cross-sectional reduction of the same and causes aradial displacement of the clamp elements from the second position tothe first position in order to release and/or unlock the closure device.The clamp elements can be spring-preloaded to provide radialdisplacement from the second position to the first position, so that onreleasing pressure of the drive medium from the pressure hose, adisplacement of the clamp elements takes place automatically through thespring action from the second position to the first position to releasethe closure device. Alternatively, the clamp elements can be radiallydisplaceable by draining the drive medium from the pressure hose,thereby producing a cross-sectional reduction of the same, to releasethe closure device from the second position to the first position.

The chain or belt arrangement can be arranged on the structure of theaircraft. The chain or belt arrangement can also be arranged on theclosure device.

The closure device according to the invention can be a radome, amaintenance or inspection hatch, or a landing-gear door. The closuredevice can also be a two-leave door using a first leaf and a secondleaf, whereby a center closure is used and is activated by the chainarrangement. Alternatively, other activation mechanisms can be providedbetween the leaves. The closure device can furthermore be a passengerdoor.

The invention also provides for a system for opening and closing astructural part arranged on a support structure, wherein the systemcomprises at least one hinged joint device for flexibly connecting thestructural part to the support structure. The at least one hinged jointdevice is arranged inside the support structure and has an axis ofrotation about which the structural part can be pivoted relative to thesupport structure during opening and closing. A locking arrangement isstructured and arranged to connect the structural part to the supportstructure in a form-locking manner when the structural part is in aclosed position. In the closed position, the locking arrangement isarranged to relieve the at least one hinged joint device.

In the closed position, the locking arrangement may be arranged to lockthe structural part to the support structure such that the at least onehinged joint device is substantially free of forces normally acting onthe at least one hinged joint device when the structural part is in aopened position. In the closed position, the locking arrangement may bearranged to lock the structural part to the support structure such thatthe at least one hinged joint device does not substantially participatein securing the structural part to the support structure.

The locking arrangement may comprise at least one first flange arrangedon the structural part and at least one second flange interacting withthe first flange and arranged on the support structure. The lockingarrangement may further comprise a locking device which interacts withthe first and second flanges, wherein, in the closed position, thelocking device locks the first and second flanges to each other. Thelocking arrangement may comprise a tightening mechanism. The tighteningmechanism may be structured and arranged to lock and unlock the lockingdevice relative to the first and second flanges. The tighteningmechanism may be structured and arranged to radially expand and contractthe locking device relative to at least one of the first and secondflanges.

The at least one hinged joint device may comprise first and second legsflexibly coupled to one another, the first leg being attached to thestructural part and the second leg being attached to the supportstructure. A joint axis that connects the first and second legs to oneanother may run at least one of along a direction of the axis ofrotation and parallel to the axis of rotation.

The at least one hinged joint device may comprise two legs flexiblycoupled to one another. The at least one hinged joint device maycomprise a first axis, a second axis, and a third axis, wherein thefirst, second and third axes intersect at a point located on the axis ofrotation. The locking arrangement may comprise a first flange arrangedon the structural part and a second flange arranged on the supportstructure. At least one of the first and second flanges may comprise acompletely closed curved flange. At least one of the first and secondflanges may comprise a continuously curved flange. At least one of thefirst and second flanges may define an outer circumference or perimeterof a passage opening. At least one of the first and second flanges maybe generally circular. Each of the first and second flanges may begenerally circular. At least one of the first and second flanges may begenerally oval. Each of the first and second flanges may be generallyoval. At least one of the first and second flanges may comprise at leastone of a plurality of partially circular sections and a plurality ofpartially oval sections. At least in the closed position, the first andsecond flanges respectively lie on a common plane.

The locking arrangement may comprise a first flange arranged on thestructural part and a second flange arranged on the support structure,whereby each of the first and second flanges comprise at least twocurved sections which lie on different planes. The locking arrangementmay comprise a first flange arranged on the structural part and a secondflange arranged on the support structure, whereby each of the first andsecond flanges comprise at least two adjacent curved sections which areoriented on different planes that interest one another.

The locking arrangement may comprise a chain or belt arrangementstructured and arranged to lock a first flange of the structural part toa second flange of the support structure. The chain or belt arrangementmay be arranged radially outside and around a circumference of the firstand second flanges. The first and second flanges may respectivelycomprise opposite facing stop surfaces which rest against one another inthe closed position. The first and second flanges may respectivelycomprise first locking surfaces which face away from each other. Thechain or belt arrangement may comprise a plurality of clamp elements.Each of the plurality of clamping elements may comprise second lockingsurfaces which interact in a form-locking manner with the first lockingsurfaces of the first and second flanges. Each of the plurality ofclamping elements may comprise second locking surfaces which engage withthe first locking surfaces of the first and second flanges. Each of theplurality of clamping elements may comprise second locking surfaceswhich sealingly engage with the first locking surfaces of the first andsecond flanges.

The chain or belt arrangement may comprise a tightening mechanismadapted to adjustable an overall length of the chain or beltarrangement. The tightening mechanism may be structured and arranged torelease or tighten the chain or belt arrangement, whereby the chain orbelt arrangement is movable between an expanded state in which the firstlocking surfaces and the second locking surfaces are not forced againsteach other so as to allow the first and second flanges to separate fromone another, and a contracted state in which the first locking surfacesand the second locking surfaces are forced against one another to lockthe structural part in the closed position. The tightening mechanism maybe structured and arranged to release or tighten the chain or beltarrangement, whereby the chain or belt arrangement is movable between anexpanded unlocked state in which the first locking surfaces and thesecond locking surfaces are not forced against each other and acontracted locked state in which the first locking surfaces and thesecond locking surfaces are forced against one another. The tighteningmechanism may be structured and arranged to release and tighten thechain or belt arrangement, whereby the chain or belt arrangement ismovable between an expanded unlocked state in which the second lockingsurfaces are not forced against the first locking surfaces and acontracted locked state in which the second locking surfaces are forcedagainst the first locking surfaces.

The chain or belt arrangement may be arranged to surround an outersurface the first and second flanges in the closed position. The chainor belt arrangement may be arranged to surround an outer circumferentialsurface the first and second flanges in the closed position. The chainor belt arrangement may comprise a flexible chain arrangement. Theflexible chain arrangement may comprise a plurality of clamp elementswhich include second locking surfaces which engage in a form-lockingmanner with first locking surfaces arranged on the first and secondflanges.

The system may further comprise a tightening mechanism structured andarranged to release and tighten the flexible chain arrangement, wherebythe chain or belt arrangement is movable between a radially expandedposition in which the second locking surfaces are not forced against thefirst locking surfaces and a radially contracted position in which thesecond locking surfaces are forced against the first locking surfaces.The tightening mechanism may be adapted to adjustable an overallcircumferential length of the flexible chain arrangement. The tighteningmechanism may be adapted to adjust an overall radial area of theflexible chain arrangement. The chain or belt arrangement may bearranged to at least partially surround the first and second flanges.

The chain or belt arrangement may be movable between a first positionwherein clamp elements of the chain or belt arrangement are arranged ina radially outward position and a second position wherein the clampelements are arranged in a radially inward position. The chain or beltarrangement may be movable between a first position wherein clampelements do not engage with each of the first and second flanges and asecond position wherein the clamp elements engage with each of the firstand second flanges, whereby the second position is radially inwardsrelative to the first position. The chain or belt arrangement may bemovable between a first position wherein clamp elements engage with eachof the first and second flanges and a second position wherein the clampelements do not engage with each of the first and second flanges,whereby the second position is radially inwards relative to the firstposition. The first and second flanges may each comprise a first conicallocking surface, wherein the chain or belt arrangement comprises secondconical locking surfaces structured and arranged to engage the firstconical locking surfaces when the structural part is in the closedposition.

The first and second flanges may each comprise a first tapered lockingsurface, wherein the chain or belt arrangement comprises second taperedlocking surfaces structured and arranged to engage the first taperedlocking surfaces when the structural part is in the closed position. Thefirst and second flanges may each comprise a first tapered lockingsurface and the chain or belt arrangement may comprise second taperedlocking surfaces structured and arranged to engage the first taperedlocking surfaces when the structural part is in the closed position,whereby the second locking surfaces generally correspond to the firstlocking surfaces. The chain or belt arrangement may remain arranged onthe first flange when the structural part is in a opened position. Thechain or belt arrangement may remain arranged on the second flange whenthe structural part is in a opened position. The chain or beltarrangement may comprise a sliding block surface which tapers outwardsand which faces towards the first flange, whereby the chain or beltarrangement expands outwardly when sliding block surface engages withthe first flange. The chain or belt arrangement may comprise clampelements having sliding block surfaces which taper outwards and whichface towards the first flange, whereby the chain or belt arrangementexpands outwardly when sliding block surfaces engage with the firstflange.

The chain or belt arrangement may comprise a sliding block surface whichtapers outwards and which faces towards the second flange, whereby thechain or belt arrangement expands outwardly when sliding block surfaceengages with the second flange. The chain or belt arrangement maycomprise clamp elements having sliding block surfaces which taperoutwards and which face towards the second flange, whereby the chain orbelt arrangement expands outwardly when sliding block surfaces engagewith the second flange. The system may further comprise a tighteningmechanism for radially expanding and contracting the chain or beltarrangement. The tightening mechanism may comprise a thread tighteneracting between respective opposite ends of the chain or belt arrangementand a helical gear for rotating the thread tightener. The helical gearmay comprise a gear wheel and a worm wheel. The gear wheel may becoupled to the thread tightener and the worm wheel is coupled to a driveelement. The drive element may be a hand twist grip. The hand twist gripmay be coupled to the worm wheel via a ball lock adapted to be unlockedvia one of an operating element and a push button. The hand twist gripmay be movable in a direction of a axis of rotation of the drive elementbetween a lowered position, in which the hand twist grip is securedagainst rotation, and another position in which the hand twist grip iscapable of rotating. The tightening mechanism may further comprise aspring arranged to move the hand twist grip, whereby the spring canmove, during unlocking, the ball lock from the lowered position to theother position.

The tightening mechanism may comprise an inflatable hose arrangedbetween clamp elements and a contact surface which is spaced from theclamping elements. The inflatable hose may be adapted to inflate via oneof a hydraulic medium and a pneumatic medium. The system may furthercomprise a pressure pump coupled to the inflatable hose, wherein thepressure pump is structured and arranged to inflate the pressure hose.Inflation of the pressure hose may cause a radial expansion of the chainor belt arrangement. Inflation of the pressure hose may cause a radialcontraction of the chain or belt arrangement.

The system may further comprise a mechanism for biasing chain or beltarrangement from an expanded state to a contracted state. The system mayfurther comprise a mechanism for biasing chain or belt arrangement froma contracted state to an expanded state. The system may further comprisea mechanism for automatically biasing chain or belt arrangement from anexpanded state to a contracted state. The system may further comprise amechanism for automatically biasing chain or belt arrangement from acontracted state to an expanded state. The chain or belt arrangement maybe adapted to automatically move a contracted state to an expandedstate. The chain or belt arrangement may be adapted to automaticallymove from an expanded state to a contracted state. The lockingarrangement may further comprise an inflatable hose, wherein clampelements of the chain or belt arrangement are radially displaceable byremoving a fluid from within the inflatable hose.

The locking arrangement may further comprise an inflatable hose, whereinclamp elements of the chain or belt arrangement are radiallydisplaceable by feeding a fluid into the inflatable hose. The vehiclemay comprise an aircraft. The structural part may comprise one of aradome, a maintenance hatch, an inspection hatch, a landing-gear doorsystem, and a passenger door.

The invention also provides for a system for locking a movably mountedstructural part to a support structure of a vehicle, wherein the systemcomprises at least one hinge pivotally connecting the structural part tothe support structure and a locking arrangement structured and arrangedto releasably connect at least one flange of the structural part to atleast one flange of the support structure. In the closed position, thelocking arrangement is arranged to lock the structural part to thesupport structure such that the at least one hinge is substantially freeof forces normally acting on the at least one hinge when the structuralpart is in a opened position.

The invention also provides for a system for locking a movably mountedstructural part to a support structure of a vehicle, wherein the systemcomprises at least one hinge pivotally connecting the structural part tothe support structure and a locking arrangement structured and arrangedto releasably connect at least one curved flange of the structural partto at least one curved flange of the support structure. The lockingarrangement comprises a chain or belt arrangement and a mechanism formoving the chain or belt arrangement between an expanded state and acontracted state.

Other exemplary embodiments and advantages of the present invention maybe ascertained by reviewing the present disclosure and the accompanyingdrawing.

BRIEF DESCRIPTION OF THE DRAWINGS

The present invention is further described in the detailed descriptionwhich follows, in reference to the noted plurality of drawings by way ofnon-limiting examples of exemplary embodiments of the present invention,in which like reference numerals represent similar parts throughout theseveral views of the drawings, and wherein:

FIG. 1 shows an isometric view of a combat aircraft in which exemplaryembodiments of the closure device according to the invention can beused;

FIG. 2 shows an isometric view of a radome of a combat aircraft as shownin FIG. 1. The radome is in the opened state and uses a first exemplaryembodiment of the invention;

FIG. 3 shows a detailed view of a hinge system of the radome shown inFIG. 2;

FIG. 4 shows a section view of the radome shown in FIG. 2 in thesymmetry plane in the closed state;

FIGS. 5 a and 5 b show detailed views of a locking device that serves tolock the closure device of an exemplary embodiment of the invention;

FIG. 6 shows a plan view of the front structural spar of the aircraftshown in FIG. 1 to which the radome (not shown in the Fig.) is attached;

FIG. 7 shows a corresponding view of the radome with a locking deviceaccording to an exemplary embodiment of the invention;

FIG. 8 shows a detailed view to explain the operational principle of thelocking device;

FIGS. 9 a-9 c show individual phases of a closing sequence of thelocking device;

FIGS. 10 a and 10 b show diagrammatic views which illustrate theoperational principle of the locking device;

FIGS. 11 a and 11 b show detail views of a tightening mechanism used foropening and closing the locking device;

FIGS. 12 a-12 c show cross-sectional views of a helical gear foroperating the locking device;

FIG. 13 shows an isometric view of a closure device in the form of anaccess flap according to a second exemplary embodiment of the inventionin the opened state;

FIG. 14 shows a plan view of the access flap shown in FIG. 13 in theclosed state from the inside of the aircraft;

FIG. 15 shows a plan view of the access flap shown in FIG. 13 in theopened state from the outside of the aircraft;

FIG. 16 shows an isometric view of a closure device in the form of anaccess flap according to a third exemplary embodiment of the inventionin the closed state, seen from the inside of an aircraft;

FIG. 17 shows a plan view of the access flap shown in FIG. 16 from theinside of the aircraft;

FIG. 18 shows a plan view of the access flap shown in FIG. 16 in theopened state from the outside of the aircraft;

FIGS. 19 a-19 c show cross-sectional views of a helical gear foroperating the locking device of the access flap shown in FIG. 16according to an exemplary embodiment of the invention;

FIG. 20 shows an isometric view of a passenger aircraft in which closuredevices according to exemplary embodiments of the invention can be used;

FIG. 21 shows an isometric view of a closure device in the form of apassenger door in the opened state seen from outside the aircraft;

FIGS. 22 a-22 c show a cross-sectional view and plan views of thepassenger door shown in FIG. 21 in closed and in opened positions;

FIG. 23 shows an isometric view of the passenger door shown in FIG. 21with a hinge mechanism according to an exemplary embodiment of theinvention;

FIG. 24 shows an isometric view of a closure device in the form of alanding-gear door comprising two leaves, in the closed position, seenfrom inside the aircraft according to another exemplary embodiment ofthe invention;

FIG. 25 shows a cross-sectional view through the two-leaved landing-geardoor of FIG. 24 along the line A-A in the closed state (indicated by asolid line) and in the opened state (indicated by a dot-dash line);

FIGS. 26 a-26 c show individual phases of a closing sequence of alocking device according to a further exemplary embodiment, and as isexplained on the basis of the landing-gear door shown in FIGS. 24 and25;

FIGS. 27 a and 27 b show isometric views of a closure device in the formof a passenger door according to a further exemplary embodiment of theinvention in the closed state, as seen from inside the aircraft or inthe opened state seen from outside the aircraft; and

FIGS. 28 a and 28 b show a detailed view in sectional form along theline B-B in FIG. 27 a according to a further exemplary embodiment of theinvention which is provided for locking the passenger door shown in FIG.27.

DETAILED DESCRIPTION OF THE PRESENT INVENTION

The particulars shown herein are by way of example and for purposes ofillustrative discussion of the embodiments of the present invention onlyand are presented in the cause of providing what is believed to be themost useful and readily understood description of the principles andconceptual aspects of the present invention. In this regard, no attemptis made to show structural details of the present invention in moredetail than is necessary for the fundamental understanding of thepresent invention, the description taken with the drawings makingapparent to those skilled in the art how the several forms of thepresent invention may be embodied in practice.

According to the invention, a closure element, which in general can be astructural part, e.g., a cover or a door, is arranged on a supportstructure in a moveable manner. The closure device, in general, isprovided to pivot the closure element arranged, e.g., on the outercontour of a support structure (e.g., a vehicle), in order to be able toopen and close and lock an access opening of the support structure. Inparticular, the support structure can be a vehicle structure into theinterior of the same one can obtain access.

The closure device according to the invention can be used, e.g., to openand close a radome arranged on an aircraft. In this example, theaircraft is the aforementioned structural part or support structure.Thus, FIG. 1 shows in isometric view a combat aircraft 1 on which theclosure device according to the invention can be used according to oneor more of the exemplary embodiments of the invention. As can be seen inFIGS. 1-3, a radome 10 is arranged to cover a front radar scanner 14 ofthe aircraft 1. One or more closure elements 20 in the form of accessflaps or hatches are provided for inspection or maintenance purposes onthe aircraft. As will be explained in detail below, landing gear doors30 can also utilize the closure device of the invention.

FIG. 2 shows in isometric view an embodiment of the closure device usedwith a radome 10. In this embodiment, the radome 10 constitutes theclosure element and the aircraft 1 constitutes the support structure. Inthe position shown in FIG. 2, the radome 10 is in the opened state. Theclosure element or the structural part in the form of the radome 10 ispivoted opened and closed by way of one or more hinged joint devices 90(see also FIG. 3). In the embodiment shown in FIG. 2, two hinged joints11, 12 are arranged on a support structure 19 of the aircraft 1. Theradome 10 can be opened and closed in order to make accessible certaininternal mechanisms. For example, the radome 10 can be opened to provideaccess for maintenance a radar scanner 14 covered by the radome 10. Whenclosed, the radome 10 forms part of the outer contour of the aircraft 1.The scanner 14 is accommodated in a passage opening 18. A first flange15 is provided on the radome 10. A second flange 16 is arranged on thesupport structure 19 of the aircraft 1. These flanges 15, 16 form,together with a chain or belt arrangement 17, a locking device withwhich the radome 10 can be fixed and securely held on the structure 19of the aircraft 1. The locking device is such that it can lock theradome 10 to the structure 19 while essentially completely relieving thehinged joints 11, 12.

In general, therefore, a first flange 15 is arranged on the closingelement or structural part 10, and a second flange 16 is arranged on thesupport or vehicle structure. These flanges 15 and 16 rest against oneanother and thereby interact in a form-locking manner in the closedposition of the closure device. In this way, the structural part 10 canclose the access opening 18 of the vehicle 1. From the point of view ofthe side to which the structural part can be pivoted into an openposition, the hinged joint device(s) are arranged inside the vehiclestructure and feature an axis of rotation X which is located outside thevehicle structure for moving the structural part 10. The locking deviceis thereby embodied such that in the closed state it locks thestructural part 10 with the support structure 19 in a form-lockingmanner while relieving the hinged joint arrangements.

According to the invention, a hinged joint arrangement 90 includes atleast one hinged joint. In the embodiment shown in FIG. 3, the hingedjoint arrangement 90 is formed by two hinged joints in the form of twoso-called pyramid gears 90 a and 90 b. Each gear 90 a and 90 b iscomposed of a first leg 91 and a second leg 92 and these legs areconnected to one another at their first end by a common axis or swivelaxis 95. The first leg 91 is also connected at its second end via afirst axis or fixed axis 93 to the radome 10. The second leg 92 isconnected at its second end via a second axis or fixed axis 94 to thestructure 19 of the aircraft 1. The first and the second axis 93, 94 arerespectively oriented at an angle to the common axis 95 which cantypically lie in the range of between approximately 40° andapproximately 80°. As can be seen at the lower hinge in FIG. 3, when theradome 10 is opened, a pivoting about a virtual axis of rotation labeledX occurs. This axis of rotation lies outside the outer contour of theaircraft 1. This also means that the axis of rotation X of thestructural part 10, about which the same can be pivoted during openingand closing, is located on the side to which the structural part 10 canbe pivoted to open.

The term pyramid gears 90 a, 90 b describes the property of the hingedjoint devices 90 a, 90 b according to which the three axes, i.e., thefirst axis 93, the second axis 94 and the center axis 95, intersect at acommon point. This point is located on the axis of rotation of theclosure device in order to avoid a mechanical incompatibility (jamming)of the hinged joint devices.

In general, the at least one hinged joint device 90 can also be embodiedas a parallelogram hinged joint device in which the hinged joint deviceis composed of two legs which are flexibly coupled to one another (seee.g., FIGS. 23 and 27). The first leg can be attached to the structuralpart and the second leg can be attached to the support structure,whereby the joint axes of the two legs run parallel and/or in thedirection of the axis of rotation X of the closure device.

In any case, the axis about which the structural part can be pivoted isarranged outside the vehicle structure from the point of view of theside to which the structural part can be pivoted into an open position.

With the hinged joint device having the form of a pyramid gear 90, thepivoting about the axis of rotation X is caused, on the one hand, byopening the first and second legs 91, 92 which rotate about their commonswivel axis 95, and on the other hand, by rotating the legs 91, 92 aboutthe fixed axes 93, 94. With the pivoting motion about the virtual axisof rotation X, the structural part or the radome 10 is fixed withrespect to the supporting structure 19 virtually in the same manner aswould be the case with a pivoting about a hinge with an actual axis ofrotation in place of the virtual axis of rotation X.

In the closed position shown in FIG. 4, it can be seen that the radome10 is attached to the structure 19 of the aircraft 1 by way of a lockingdevice. Details A and B are shown in FIGS. 5 a and 5 b. The lockingdevice includes a first flange 15 that is arranged on the structuralpart or radome 10 and a second flange 16 that is provided and/orarranged on the structure 19. The flanges 15, 16 are embodied such thatthey interact in a form-locking manner. Furthermore, the locking devicefeatures a blocking or locking arrangement 17 that can be embodied, inparticular, as a chain or belt arrangement (see FIGS. 5 a, 5 b). In theclosed state, the locking arrangement 17 provides a form-closed lockingbetween the first flange 15 and the second flange 16. The blockingdevice or the chain or belt arrangement also includes a tighteningmechanism 70 with which the chain or belt arrangement can be tightenedonto or loosened from the flanges 15, 16.

FIGS. 6 and 7 show in plan view the second flange 16 provided on thestructure 19 of the aircraft 1. The first flange 15 provided on theradome 10 together with the blocking device or chain or belt arrangement17 and the tightening mechanism 70 is also shown. The chain or beltarrangement utilizes a sliding cam SC. The first flange 15 and thesecond flange 16 respectively form a curve running in a completelyclosed manner. In this exemplary embodiment, the completely closed curveis in the form of a complete circle. As is also evident in FIG. 7, thefirst flange 15 arranged on the radome 10 limits the circumference ofthe passage opening 18 that is provided for the radar scanner 14 to passthrough.

The operational principle of the locking device formed by the firstflange 15, the second flange 16 and the blocking device in the form of achain or belt arrangement 17 will now be explained in more detail withreference to FIGS. 8 through 10. In the closed position of the closuredevice, and thus in the closed position of the radome 10, the firstflange 15 and the second flange 16 rest against one another, see FIGS. 8and 9 c. As a result, the stop surfaces 56 and 57, which are arranged toface one another (see FIG. 9 a) contact one another. A plurality ofclamp elements 61 are provided on a flexible chain or belt arrangement.These clamp elements 61 are connected to one another by the chain orbelt arrangement 60 (see FIGS. 9 a and b and FIG. 10 a and 10 b). Theclamp elements 61 feature respective second locking surfaces 64, 65which interact in a form-locking manner with first locking surfaces 52,53 provided on the sides of the flanges 15, 16 facing away from oneanother (see FIGS. 9 a-9 c).

The tightening mechanism 70, which in FIG. 10 is indicated onlydiagrammatically by arrows, is used to changed an overall length of thechain or belt arrangement 17 between an extended and/or expanded state,in which the first locking surfaces 52, 53 of the first flange 15 or ofthe second flange 16 and the second locking surfaces 64, 65 of the clampelements 61 are free of one another so as to release the closure device10, and a contracted state in which the first locking surfaces 52, 53 ofthe first and second flanges 15, 16 and the second locking surfaces 64,65 of the clamp elements 61 are fixed and/or engage against one anotherto provide for locking engagement.

As FIGS. 8 and 9 show, the first locking surfaces 52, 53 provided on theflanges 15, 16 form an outer conical cross-sectional shape which tapersoutwards in the radial direction. The second locking surfaces 64, 65provided on the clamp elements 61 form an inner conical cross-sectionalshape which tapers outwards in the radial direction and which generallymatches the cross-sectional shape of the first locking surfaces 52, 53.As a result, when the locking arrangement 17 and flanges 15 and 16 arein the position shown in FIGS. 9 c and 10 a, the closure device can besaid to be locked a form-locking manner.

The chain or belt arrangement 17, which includes the chain or beltelement 60 and the clamp elements 61 arranged thereon, is also arrangedin a fixed manner with regard to one of flanges. In the exemplaryembodiment shown, this flange is the first flange 15. As a result, theclamp elements 61 have, on the side facing the second flange 16, asliding block surface 66 which is tilted or tapered outwards. In thisway, the clamp elements 61 can, during closing of the locking device ormovement of the flanges 15 and 16 towards one another, can be displacedradially outwards to engage the first locking surface 53 of the flangebehind the assigned second locking surface 65 of the clamp elements 61.

The tightening mechanism 70, as can be seen in FIGS. 11 a and 11 n, caninclude a thread tightener acting between respective opposite ends 62,63 of the chain or belt element 60. The thread tightener can include athreaded pin 71 arranged in a generally central position. The threadedpin 17 includes oppositely directed threads (e.g., right hand threadsand left hand threads or left hand threads and right hand threads) onopposite ends. The thread tightener also includes thread blocks 72 and73 arranged at the ends 62 or 63 of the chain or belt element 60, asknown per se. A helical gearing is used for operating the threadtightener which contains a gear wheel 74 coupled to the threaded pin 71in a rotationally locked manner and a worm wheel 75 engaged therewithand coupled to a drive element 80.

By way of non-limiting example, the drive element 80 is a hand twistgrip that is coupled to the worm wheel 75 via a ball block. See FIGS. 12a-12 c. The ball block is composed of an inner casing 87 provided with agroove 82, an outer casing 88 provided with a groove 83 and severalballs 81 arranged in between. These balls 81 are deposited in recesses85 that are embodied in the body 80 a of the hand twist grip 80. Theinner casing 87 is provided with a push button 84 arranged on an outsideand accessible to an operator (see FIG. 12 a). The push button 84, whenpressed against the pressure of a spring 86, acts to release the balls81 (see FIG. 12 b). In this way, the hand twist grip 80 is released formovement outwards due to the action of a spring 89 (see FIG. 12 c). As aresult, the hand twist grip is displaceable in the direction of its axisof rotation between a lowered position, in which it is secured againstrotation, and a raised or not lowered position in which it is releasedfor rotation. In this latter position, the tightening mechanism 70 canbe activated via the helical gearing 74, 75 and thus the chain or beltelement 60 can be released.

FIGS. 13 through 15 show a second exemplary embodiment of the inventionin which the structural part 20 is a maintenance or inspection cover. Apassage opening 28 is provided in the vehicle structure 29 which againis an aircraft. This opening 28 can be closed with the cover 20. Thecover 20 is connected to the structure 29 by hinges 21, 22, which can bethe previously mentioned pyramid gears. Through the use of these pyramidgears a virtual axis of rotation lying outside the outer skin of theaircraft is again formed about which the cover 20 can be opened. In thisembodiment, however, an opening of the cover 20 is facilitated by resortto a gas pressure mechanism 23 which that acts between the hinges 21,22. Through the spring force of the gas pressure mechanism 23, the legsof the pyramid gearings are pressed apart in the area of their swivelaxis. This produces an opening movement and causes an opening of thecover 20.

As with the previous embodiment, a first flange 25 is arranged on thestructural part or cover 20 and a second flange 26 is arranged on thestructure 29 of the aircraft. A locking device in the form of chain orbelt arrangement 27 is used essentially in the same way as described forthe first exemplary embodiment with reference to FIGS. 8 through 12.Here, too, the operation of the chain or belt arrangement 27 takes placeby way of a tightening mechanism 70 as previously described.

In the third exemplary embodiment shown in FIGS. 16 through 18, aninspection or maintenance cover 30 is illustrated. The cover 30 it isattached to the aircraft structure 39 by way of a hinge arrangementwhich includes hinges 31, 31 a, 32, 32 a. Here, too, the hinges 31, 31a, 32, 32 a are pyramid gears of the previously described type.

A gas pressure mechanism 33 is arranged between the springs 31, 31 a.The mechanism 33 provides the opening motion of the cover 30, in thesame way as was previously described with reference to the secondexemplary embodiment. In contrast to the second exemplary embodiment,however, here two first flanges 35, 35 a are provided on the cover 30which interact with two second flanges 36, 36 a that are provided on thestructure 39 of the aircraft having a passage opening 38. A chain orbelt arrangement 37, 37 a is thus provided on each of the first flanges35, 35 a. Each of these arrangements 37 and 37 a can be operated by wayof a common tightening mechanism 70.

The tightening mechanism 70 is shown in detail in FIGS. 19 a-19 c. Thegeneral operation is the same as with the tightening mechanism explainedwith regard to FIGS. 12 a-12 c. However, the geometry is slightlydifferent with respect to the position of the closure devices 20; 30.FIG. 19 b also illustrates a ball movement BM.

Finally, FIGS. 20-23 shows a passenger aircraft 2 which uses a fourthexemplary embodiment of the closure device 45 according to the inventionfor opening and closing a passenger door 40.

The passenger door 40 is shown in more detail in FIGS. 21 through 23. Aswas the case in previous embodiments, a passage opening 48 is embodiedin the structure 49 of the outer wall of the aircraft 2. This opening 48is limited on its circumference by a flange 46. The closure device,which is partially arranged on the passenger door 40, includes threeflanges 45 a, 45 b, 45 c (see in particular FIGS. 22 a and 22 c). Theflange 45 constitutes a first flange provided on the passenger door 40.A second flange 46 is provided on the structure 49 of the aircraft 2.Each of these flanges 45 and 46 are composed of several flange portions.In the example shown, these partial flanges are circular flanges. As canbe seen in FIG. 22 a, the flanges 45 a, 45 b, 45 c (and also the flanges46 a, 46 b, 46 c) lie in different planes which intersect where theparts of the flanges 45, 46 touch one another. A chain or beltarrangement 47 has portions 47 a, 47 b and 47 c which are arranged onthe flanges 45 a, 45 b, 45 c of the first flange 45. This arrangement 47is used to lock the flanges 45 and 46 to each other during closing ofthe door 40. The operation is essentially the same as explained withreference to FIGS. 8 and 9. Here, too, a tightening mechanism 70 isprovided that is used for the common operation of the same.

In this fourth exemplary embodiment, the hinge 41, through which thepassenger door 40 is connected to the structure 49 of the aircraft 2,has the form of a parallelogram hinged joint device in which the firstaxis and the second axis and the center axis run parallel to oneanother.

FIGS. 24 through 26 show another exemplary embodiment of a closuredevice according to the invention. In this embodiment, the closureelement is a two-leaved landing-gear door. The landing-gear doorcomprises a first leaf 110 and a second leaf 110 a. Each leaf isrespectively attached by hinges 111, 112, 113 and 111 a, 112 a, 113 a tothe structure 119 of the aircraft. In this way, the door can be mountedin a pivoted manner.

The hinges 111, 112, 113, 111 a, 112 a, 113 a are formed as pyramidgears of the type described above, and again utilize a virtual axis ofrotation X that lies outside the outer contour of the aircraft. As thesectional representation of FIG. 25 shows, an opening of the leaves 110,110 a of the landing-gear door takes place about the virtual axis ofrotation X, whereby a reciprocal locking and unlocking of the twolanding-gear door leaves 110, 110 a is ensured via a center closure 114.When the landing-gear door 110, 110 a is opened, a passage opening 118is available and/or used for, e.g. the wheel of an aircraft landing gearto pass through.

Respective first flanges 115, 115 a are provided on the outercircumference of the leaves 110, 110 a. These flanges 115, 115 ainteract with second flanges 116, 116 a arranged on the circumference ofthe passage opening 118 on the structure 119. This interaction and theuse of a locking device act to lock the landing-gear door. The firstflanges 115, 115 a also interact with the centrally arranged centerclosure 114.

As the enlarged detailed representation in FIGS. 26 a-26 c show, thefirst and second flanges 115, 115 a, 116, 116 a have on their sidesfacing one another respective stop surfaces 156 or 157 that rest againstone another in the closed state of the landing-gear door leaves 110, 110a. On their sides facing away from one another, they have first lockingsurfaces 152 or 153 (see FIG. 26 b). A number of clamp elements 161 of achain arrangement 117 (only one of which is shown in section) havesecond locking surfaces 164 or 165 that interact in a form-lockingmanner with the first locking surfaces 152 or 153 provided on the firstand second flanges 115, 115 a, 116, 116 a. The chain arrangement 117 isarranged to run in the radial direction inside the first and secondflanges 115, 115 a, 116, 116 a.

The clamp elements 161 of the chain arrangement 117 are adjustable intheir radial position with respect to the center of the leaves 110, 110a of the landing-gear door between a first position lying radiallyfurther inside, in which the first locking surfaces 152, 153 of thefirst and second flanges 115, 115 a, 116, 116 a and the second lockingsurfaces 164, 165 of the clamp elements 161 to release the landing-geardoor 110, 110 a are free of one another (see FIGS. 26 b-26 c), and asecond position lying radially further outside, in which the firstlocking surfaces 152, 153 of the first and second flanges 115, 115 a,116, 116 a and the second locking surfaces 164, 165 of the clampelements 161 which lock the landing-gear door 110, 110 a are fixedagainst one another (see FIG. 26 a).

As can be further seen from FIG. 26, a pressure hose 160, which can beacted on by a hydraulic or pneumatic work medium, is arranged betweenthe clamp elements 161 and a stop surface 160 a lying further radiallyinwards. The clamp elements 161 can be displaced by the hose 160. Thepressure hose 160 is acted on with the drive medium through a pressuremedium pump 117 a (see FIG. 24). When the pressure hose 160 is acted onwith the drive medium, a cross-sectional enlargement of the pressurehose 160 causes a radial displacement of the clamp elements 161 to occurfrom the first position lying radially further inwards (see FIG. 26 band 26 c) to the second position lying radially further outwards (seeFIG. 26 a). In the second position, the landing-gear door leaves 110,110 a are locked to the aircraft structure 119. When the drive mediumflows out of the pressure hose 160, with a cross-sectional reduction ofthe hose 160 causes a radial displacement of the clamp elements 161 inthe opposite direction from the second position lying radially furtheroutwards (see FIG. 26 a) to the first position lying radially furtherinwards so as to release the lock (see FIGS. 26 b and 26 c). This latterdisplacement from the locked position to the opened position can beachieved by, e.g., ensuring that the clamp elements 161 arespring-preloaded for a radial displacement from the second position intothe first position. In this way, a relief of pressure of the drivemedium from the pressure hose 160 causes a displacement of the clampelements 161 through a spring action. Such movement thus takes placefrom the second position lying radially further outwards to the firstposition lying radially further inwards to release the landing-gear door110, 110 a. The clamp elements 161 can thus be displaced by activedraining of the drive medium from the pressure hose 160 withcross-sectional reduction of the same to release the landing-gear door110, 110 a from the second position lying radially further outwards intothe first position lying radially further inwards.

FIGS. 27 a and 27 b show as a further exemplary embodiment a passengerdoor 140 that is supported in the structure 149 of an aircraft 2 by wayof at least one parallelogram hinged joint arrangement 141 which usestwo legs coupled flexibly to one another with a first axis 93, a secondaxis 94 and a center axis 95 that each run parallel to one another. Asecond flange 146 is provided on the structure 149 of the aircraft 2.The flange 146 interacts with a first flange 145 provided on thepassenger door 140. When the passenger door 140 is opened, one can gainaccess to a passage opening 148. A chain arrangement 147 is utilizedand, as with the previous embodiments, follows a circumference of thepassage opening 148. The arrangement 147 is provided on the secondflange 146, which chain arrangement interacting with the first flange145 and the second flange 146 causes a locking and unlocking of thepassenger door 140.

As the enlarged detailed representation in FIGS. 28 a and 28 b show, thefirst and second flanges 145, 146 have stop surfaces 156, 157respectively on the sides facing one another which rest against oneanother when the passenger door 140 is closed. On sides facing away fromone another, first locking surfaces 152 and 153 are utilized (see FIG.28 b).

A number of clamp elements 161 of the flexible chain arrangement 147(only one of which is shown in section) are used and they have secondlocking surfaces 164 and 165 that interact in a form-locking manner withthe first locking surfaces 152 and 153 provided on the first and secondflanges 145 and 146. The clamp elements 161 of the chain arrangement147, which are arranged to surround the passage opening 148 on thestructure 149 of the aircraft 2, are adjustable in their radial positionbetween a first position lying radially further outwards, in which thefirst locking surfaces 152, 153 of the first and second flanges 145,146, and the second locking surfaces 164, 165 of the clamp elements 161are free of one another to release the passenger door 140 (see FIG. 28b), and a second position lying radially further inwards, in which thefirst locking surfaces 152, 153 of the first and second flanges 145, 146and the second locking surfaces 164, 165 of the clamp elements 161 arefixed against one another to lock the passenger door 140 (see FIG. 28a). The chain arrangement 147 is arranged to run radially outside aroundthe circumference of the first and second flanges 145, 146.

As in the previous exemplary embodiment of FIG. 26, a pressure hose 160that can be acted on by a hydraulic or pneumatic drive medium isprovided between the clamp elements 161 and a contact surface 160 alying further outside radially displaced thereto. A pressure medium pump147 a is used to act on the pressure hose 160 with the drive medium (seeFIG. 27 a). When the pressure hose 160 is acted on with the drivemedium, resulting in a cross-sectional enlargement of the same, a radialdisplacement of the clamp elements 161 from the first position lyingradially further outwards (see FIG. 28 b) to the second position lyingradially further inwards (see FIG. 28 a) occurs and locks the passengerdoor 140. When the drive medium flows out of the pressure hose 160,resulting in a cross-sectional reduction, a radial displacement of theclamp elements 161 in the opposite direction takes place from the secondposition lying radially further inwards to the first position lyingradially further outwards to release the passenger door 140.

It is noted that the foregoing examples have been provided merely forthe purpose of explanation and are in no way to be construed as limitingof the present invention. While the present invention has been describedwith reference to an exemplary embodiment, it is understood that thewords which have been used herein are words of description andillustration, rather than words of limitation. Changes may be made,within the purview of the appended claims, as presently stated and asamended, without departing from the scope and spirit of the presentinvention in its aspects. Although the present invention has beendescribed herein with reference to particular means, materials andembodiments, the present invention is not intended to be limited to theparticulars disclosed herein; rather, the present invention extends toall functionally equivalent structures, methods and uses, such as arewithin the scope of the appended claims.

LIST OF REFERENCE NUMBERS

-   1 Combat aircraft-   2 Passenger aircraft-   10 Radome-   11 Hinge-   12 Hinge-   14 Radome-   15 First flange-   16 Second flange-   17 Chain or belt arrangement-   18 Passage opening-   19 Structure-   20 Inspection hatch-   21 Hinge-   22 Hinge-   22 Gas pressure spring-   25 First flange-   26 Second flange-   27 Chain or belt arrangement-   28 Passage opening-   29 Structure-   30 Inspection hatch-   31, 31 a Hinge-   32, 32 a Hinge-   35, 35 a First flange-   36, 36 a Second flange-   37 Chain or belt arrangement-   38 Passage opening-   39 Structure-   40 Passenger door-   41 Hinge-   45 First flange-   46 Second flange-   47 Chain or belt arrangement-   48 Passage opening-   49 Structure-   52 First locking surface-   53 First locking surface-   54 Second locking surface-   55 Second locking surface-   56 Stop surface-   57 Stop surface-   60 Chain or belt element-   61 Clamp element-   62 End-   63 End-   64 Second locking surface-   65 Second locking surface-   66 Sliding block surface-   79 Tightening mechanism-   71 Threaded pin-   72 Thread block-   73 Thread block-   74 Gear wheel-   75 Drive element, hand twist grip-   80 a Body-   80 a Ball-   82 Groove-   83 Groove-   84 Push button-   85 Recess-   86 Spring-   87 Inner casing-   88 Outer casing-   89 Spring-   90 Pyramid gear-   90 a, 90 b Hinged joint-   91 First leg-   92 Second leg-   93 First fixed axis-   94 Second fixed axis-   95 Swivel axis-   110, Landing-gear door-   110 a-   111, Hinge-   111 a-   112, Hinge-   112 a-   113, Hinge-   113 a-   114 Center closure-   115, First flange-   115 a-   116, Second flange-   116 a-   117 Chain arrangement-   117 a Pressure medium pump-   118 Passage opening-   119 Structure-   140 Passenger door-   141 Hinge-   145 First flange-   146 Second flange-   147 Chain arrangement-   147 a Pressure medium pump-   148 Passage opening-   149 Structure-   152, 153 First locking surface-   156 Stop surface-   157 Stop surface-   160 Pressure hose-   160 a Stop surface-   161 Clamp element-   164, 165 Second locking surface

1. A system for opening and closing a structural part arranged on asupport structure, the system comprising: at least one hinged jointdevice for flexibly connecting the structural part to the supportstructure; the at least one hinged joint device being arranged insidethe support structure and having an axis of rotation about which thestructural part can be pivoted relative to the support structure duringopening and closing; and a locking arrangement structured and arrangedto connect the structural part to the support structure in aform-locking manner when the structural part is in a closed position, inthe closed position, the locking arrangement being arranged inside thesupport structure and is arranged to relieve the at least one hingedjoint device; the locking arrangement comprising a chain or beltarrangement structured and arranged to lock a first flange of thestructural part to a second flange of the support structure; and atightening mechanism for radially expanding and contracting the chain orbelt arrangement, wherein the tightening mechanism comprises aninflatable hose arranged between clamp elements and a contact surfacewhich is spaced from the clamping elements.
 2. The system of claim 1,wherein the inflatable hose is adapted to inflate via one of a hydraulicmedium and a pneumatic medium.
 3. The system of claim 2, furthercomprising a pressure pump coupled to the inflatable hose, wherein thepressure pump is structured and arranged to inflate the pressure hose.4. The system of claim 3, wherein inflation of the pressure hose causesa radial expansion of the chain or belt arrangement.
 5. The system ofclaim 3, wherein inflation of the pressure hose causes a radialcontraction of the chain or belt arrangement.
 6. A system for openingand closing a structural part arranged on a support structure, thesystem comprising: at least one hinged joint device for flexiblyconnecting the structural part to the support structure; the at leastone hinged joint device being arranged inside the support structure andhaving an axis of rotation about which the structural part can bepivoted relative to the support structure during opening and closing;and a locking arrangement structured and arranged to connect thestructural part to the support structure in a form-locking manner whenthe structural part is in a closed position, in the closed position, thelocking arrangement being arranged inside the support structure and isarranged to relieve the at least one hinged joint device; and thelocking arrangement comprising a chain or belt arrangement structuredand arranged to lock a first flange of the structural part to a secondflange of the support structure, wherein the locking arrangement furthercomprises an inflatable hose, wherein clamp elements of the chain orbelt arrangement are radially displaceable by removing a fluid fromwithin the inflatable hose.
 7. A system for opening and closing astructural part arranged on a support structure, the system comprising:at least one hinged joint device for flexibly connecting the structuralpart to the support structure; the at least one hinged joint devicebeing arranged inside the support structure and having an axis ofrotation about which the structural part can be pivoted relative to thesupport structure during opening and closing; and a locking arrangementstructured and arranged to connect the structural part to the supportstructure in a form-locking manner when the structural part is in aclosed position, in the closed position, the locking arrangement beingarranged inside the support structure and is arranged to relieve the atleast one hinged joint device; and the locking arrangement comprising achain or belt arrangement structured and arranged to lock a first flangeof the structural part to a second flange of the support structure,wherein the locking arrangement further comprises an inflatable hose,wherein clamp elements of the chain or belt arrangement are radiallydisplaceable by feeding a fluid into the inflatable hose.